Volume 5, Juin 2013Progress in Flight Physics
|Page(s)||349 - 362|
|Section||Chapter Five. Shock interaction|
|Published online||14 June 2013|
Supersonic laminar separated flow structure at a ramp for a free-stream mach number of 6
Khristianovich Institute of Theoretical and Applied Mechanics 4/1 Institutskaya Str., Novosibirsk 630090, Russia
2 TsAGI 1 Zhukovsky Str., Zhukovsky, Moscow Region 140180, Russia
A three-dimensional (3D) structure of a separated flow in a compression corner at a free-stream Mach number M = 6 is studied. The model is a flat plate with an almost sharp leading edge on which a 30° ramp is mounted. The spanwise size of the model is equal to the length of the plate from the leading edge to the ramp. The angle of attack is varied from 0° to 15°. The shock wave structure of the flow near the model is shown. The existence of a thin high total pressure layer (dynamic layer) is found. The dynamic layer is located above the boundary layer on the ramp, downstream from the reattachment line. The existence streamwise vortices near the reattachment line is shown. The measured spectra of the wall pressure fluctuations in the reattachment region are presented.
© Owned by the authors, published by EDP Sciences, 2013
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